CN113898607A - Vane intersecting line of impeller machine, design method of vane, and vane of impeller machine - Google Patents

Vane intersecting line of impeller machine, design method of vane, and vane of impeller machine Download PDF

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CN113898607A
CN113898607A CN202111168465.4A CN202111168465A CN113898607A CN 113898607 A CN113898607 A CN 113898607A CN 202111168465 A CN202111168465 A CN 202111168465A CN 113898607 A CN113898607 A CN 113898607A
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blade
outer ring
point
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CN113898607B (en
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黄建华
周康
赵斌
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Jiangsu XCMG Construction Machinery Institute Co Ltd
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/18—Rotors
    • F04D29/22—Rotors specially for centrifugal pumps
    • F04D29/24—Vanes
    • F04D29/242—Geometry, shape
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/384—Blades characterised by form
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/388—Blades characterised by construction
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/17—Mechanical parametric or variational design

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Abstract

The invention discloses a method for designing a blade intersecting line of impeller machinery, which comprises the following steps: determining a two-dimensional blade outer ring molded line of the blade according to a two-dimensional blade outer ring skeleton line, and determining an intersecting line of the blade and an outer ring according to the blade outer ring molded line and inner surface parameters of the outer ring; calculating a three-dimensional blade outer ring skeleton line corresponding to the two-dimensional blade outer ring skeleton line on the inner surface of the outer ring according to the two-dimensional blade outer ring skeleton line and the inner surface parameters of the outer ring; determining a projection vector according to the three-dimensional blade outer ring skeleton line, determining a projection plane according to the projection vector, and projecting the three-dimensional blade outer ring skeleton line on the projection plane; a projection point set of the three-dimensional blade outer ring skeleton line on a projection plane is taken to determine a two-dimensional blade inner ring skeleton line; and determining a two-dimensional blade inner ring profile of the blade according to the determined two-dimensional blade inner ring skeleton line, and determining the intersection line of the blade and the inner ring according to the two-dimensional blade inner ring profile, the parameters of the projection surface and the outer surface parameters of the inner ring.

Description

Vane intersecting line of impeller machine, design method of vane, and vane of impeller machine
Technical Field
The invention relates to the field of impeller machinery, in particular to a blade intersecting line of the impeller machinery, a design method of the blade and the blade of the impeller machinery.
Background
Turbomachines are widely used in engineering applications, including fans, torque converters, water pumps, compressors, etc. The impeller machine generally comprises a blade cascade, an outer ring positioned on the outer side of the blade cascade and an inner ring positioned on the inner side of the blade cascade, wherein the blade cascade comprises a plurality of blades which are periodically arranged around a rotating shaft, the inner ring comprises a front disc and an outer ring comprises a rear disc, a channel formed by the blade cascade, the front disc and the rear disc forms a flow channel for fluid to flow, and the mutual conversion of mechanical energy and fluid kinetic energy is realized through the interaction of the blade cascade and fluid. The blades of the blade cascade are core components of the impeller machinery, and the performance of the impeller machinery is directly influenced by the quality of the design of the blades. The shape of the blade is greatly different according to different application occasions, and comprises a two-dimensional straight plate blade, a non-uniform thickness three-dimensional twisted blade and the like. The patent application with Chinese patent application number 201310028487.X provides an airfoil represented by an analytic function and a generation method thereof, wherein a single ring surface of the airfoil is represented by upper and lower profile analytic functions. The patent application of the Chinese patent application number 201710523249.4 discloses a multi-wing centrifugal fan blade, wherein the inlet end curve of the blade profile is a logarithmic spiral line, and the outlet end profile is an arc line. The Chinese patent application No. 201510036723.1 discloses a method for constructing a two-dimensional blade profile of a hydraulic torque converter based on a Bezier curve, and discloses that a two-dimensional blade profile of an inner ring of a pump impeller blade is constructed by using the Bezier curve through a given circle of the hydraulic torque converter, and then the two-dimensional blade profile is constructed by using the two-dimensional blade profile to construct the thickness distribution of the blade, so that the two-dimensional blade profile is obtained. The Chinese patent application No. 201510036723.1 discloses a method for constructing a two-dimensional blade profile of a hydraulic torque converter based on a Bezier curve, and discloses that a two-dimensional blade profile of an inner ring of a pump impeller blade is constructed by using the Bezier curve through a given circle of the hydraulic torque converter, and then the two-dimensional blade profile is constructed by using the two-dimensional blade profile to construct the thickness distribution of the blade, so that the two-dimensional blade profile is obtained. The Chinese patent application No. 201410220625.9 discloses a vane model of a hydraulic torque converter based on a Confucius-fusi type line, which discloses that a two-dimensional vane inner ring molded line and a two-dimensional vane outer ring molded line of a unit vane are constructed through the Confucius-fusi type line, then a three-dimensional vane inner ring curve and a three-dimensional vane outer ring curve are constructed according to parameters of a given circulation circle, and finally the vane model is formed.
Disclosure of Invention
The invention aims to provide a design method of a blade intersecting line of an impeller machine, which can be used for constructing a proper blade intersecting line of the impeller machine, thereby being beneficial to ensuring the adaptability, diversity, flexibility and good manufacturability of the blade.
The invention discloses a method for designing a blade intersecting line of impeller machinery, wherein the impeller machinery comprises an outer ring, an inner ring positioned on the inner side of the outer ring and blades connected between the outer surface of the inner ring and the inner surface of the outer ring, and the method for designing the blade intersecting line of the impeller machinery comprises the following steps:
giving two-dimensional blade outer ring bone line, inner surface parameters of the outer ring and outer surface parameters of the inner ring;
determining a two-dimensional blade outer ring molded line of the blade according to the two-dimensional blade outer ring skeleton line, and determining an intersecting line of the blade and the outer ring according to the two-dimensional blade outer ring molded line and the inner surface parameter of the outer ring;
calculating a three-dimensional blade outer ring skeleton line corresponding to the two-dimensional blade outer ring skeleton line on the inner surface of the outer ring according to the two-dimensional blade outer ring skeleton line and the inner surface parameters of the outer ring;
determining a projection vector according to the three-dimensional blade outer ring skeleton line, determining a projection plane according to the projection vector, and projecting the three-dimensional blade outer ring skeleton line on the projection plane;
a projection point set of the three-dimensional blade outer ring skeleton line on the projection surface is taken to determine a two-dimensional blade inner ring skeleton line;
determining a two-dimensional blade inner ring molded line of the blade according to the determined two-dimensional blade inner ring skeleton line, and determining an intersection line of the blade and the inner ring according to the two-dimensional blade inner ring molded line, the parameters of the projection surface and the outer surface parameters of the inner ring.
In some embodiments, determining a projection vector from the three-dimensional outer blade ring skeleton line comprises:
determining an extreme point of the three-dimensional blade outer ring skeleton line, connecting a starting point and an end point of the three-dimensional blade outer ring skeleton line to obtain a first line segment, and drawing a first straight line which is perpendicular to the connecting line and intersects with the first point through the extreme point;
radius r is made through the extreme point in a plane perpendicular to the first line1A first circle of radius r passing through the first point in a plane perpendicular to the first line2Second circle of (1), wherein r1Less than r2And r is1And r2And the length of each line segment is less than half of the length of the first line segment, a second point is taken in the first circle, a third point is taken in the second circle, and a vector obtained by connecting the second point and the third point is determined as the projection vector.
In some embodiments, let the extreme point coordinate be (x)M，yM，zM) Let the coordinates of the first point be (x)H，yH，zH) Connecting the extreme point and the first point to obtain a first vector, and setting the space coordinate of the first vector as (V)x，Vy，Vz) Let the coordinates of the second point be (x)1，y1，z1) Let the coordinate of the third point be (x)2，y2，z2) Wherein:
Figure BDA0003288608610000031
Figure BDA0003288608610000032
y1∈(yM-r1，yM+r1)，x2∈(xH-r2，xH+r2)，y2∈(yH-r2，yH+r2)。
in some embodiments, determining a projection vector from the three-dimensional outer blade ring skeleton line comprises:
determining an extreme point of the three-dimensional blade outer ring skeleton line, connecting a starting point and an end point of the three-dimensional blade outer ring skeleton line to obtain a first line segment, and drawing a first straight line which is perpendicular to the connecting line and intersects with the first point through the extreme point;
and passing the extreme point to make a second straight line towards a deflection angle alpha on one side of the first straight line in a plane determined by the first straight line and the first line segment, and to make a third straight line towards a deflection angle beta on one side of the first straight line in a plane perpendicular to the plane determined by the first straight line and the first line segment, wherein the second straight line and the first line segment are intersected at a fourth point, the extreme point and the fourth point are connected to obtain a second vector, a third vector is obtained according to the third straight line, and the projection vector is equal to the vector sum of the second vector and the third vector.
In some embodiments, the two-dimensional blade outer ring bone line is a bezier curve.
The invention discloses a method for designing a blade of an impeller machine in a second aspect, which comprises a method for designing a blade intersecting line of any impeller machine.
In some embodiments, further comprising: and sweeping the intersecting line of the blade and the inner ring and the intersecting line of the blade and the outer ring by using a straight line to obtain the blade of the impeller machine.
The third aspect of the invention discloses a blade of impeller machinery, which is designed by applying the design method of the blade of impeller machinery.
In some embodiments, the impeller machine blades comprise blades of an impeller of a torque converter, the outer ring comprises an impeller casing, and the inner ring comprises an impeller guide ring; or the blades of the impeller machine comprise blades of a turbine of a hydrodynamic torque converter, the outer ring comprises a turbine casing, and the inner ring comprises a turbine guide ring
According to the design method of the blade intersecting line of the impeller machine, the three-dimensional blade outer ring intersecting line is calculated by utilizing the two-dimensional blade outer ring intersecting line, then the two-dimensional blade inner ring intersecting line is determined by utilizing the projection after the proper projection vector projection is found for the three-dimensional blade outer ring intersecting line, the proper and coordinated two-dimensional blade inner ring intersecting line can be conveniently and effectively obtained, the blade intersecting line of the impeller machine obtained by the method is more reasonable, coordinated and effective, and the manufactured blade has good mechanical property and good manufacturability.
Other features of the present invention and advantages thereof will become apparent from the following detailed description of exemplary embodiments thereof, which proceeds with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without limiting the invention. In the drawings:
FIG. 1 is a flow chart of a method of designing a bucket intersection line of a turbomachinery of an embodiment of the present invention;
FIG. 2 is a schematic view of a portion of another embodiment of the present invention;
FIG. 3 is a schematic diagram of a projection vector determined by a method for designing a blade intersecting line of a turbo machine according to still another embodiment of the present invention;
fig. 4 is a schematic diagram of a projection vector determination method for designing a blade intersecting line of an impeller machine according to still another embodiment of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
For ease of description, spatially relative terms, such as "over", "above", "on", "upper surface", "over", and the like, may be used herein to describe one element or feature's spatial relationship to another element or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above" may include both an orientation of "above" and "below". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
As shown in fig. 2, the impeller machinery includes an outer ring 1, an inner ring 5 located inside the outer ring 1, and blades connected between an outer surface of the inner ring 5 and an inner surface of the outer ring 1, the blades include a blade outer ring 2, a blade inner ring 6, a blade leading edge 4, and a blade trailing edge 8, the blade outer ring 2 is an outer surface of the blade located radially outside, that is, an intersecting surface of the blade and the outer ring 1, and an outer contour of the blade outer ring 2, that is, a intersecting line of the blade and the outer ring 1. The blade inner ring 6 is the inner surface of the blade at the radial inner side, namely the intersection surface of the blade and the inner ring 5, and the outer contour of the blade inner ring 6 is the intersection line of the blade and the inner ring 5.
The impeller machine of the embodiment comprises a fan, a hydraulic torque converter, a water pump, a gas compressor and the like. When the impeller machine is a torque converter, and when the blades shown in fig. 2 are impeller blades, the outer ring 1 is an impeller casing, the inner ring 5 is an impeller guide ring, and fluid enters from the inlet 3 on the side of the leading edge 4 of the blade, and flows out from the outlet 7 on the side of the trailing edge 8 of the blade into the turbine under the centrifugal action of the blades of the impeller. The direction Z shown in fig. 2 indicates the direction of the rotation axis of the pump wheel, and the direction R indicates the radial direction of the pump wheel.
The method for designing the blade intersecting line of the impeller machinery comprises the following steps:
the two-dimensional blade outer ring bone line, the inner surface parameter of the outer ring and the outer surface parameter of the inner ring are given.
The two-dimensional blade outer ring skeleton line can adopt an empirical skeleton line type according to the prior experience, and can also be constructed by a Bezier curve.
And determining a two-dimensional blade outer ring molded line of the blade according to the two-dimensional blade outer ring skeleton line, and determining an intersecting line of the blade and the outer ring 1 according to the blade outer ring molded line and the inner surface parameters of the outer ring 1.
The inner surface parameters of the outer ring 1 include parameter information such as the shape, angle, size distribution, etc. of the inner surface. After obtaining two-dimensional blade outer ring molded lines, mapping the two-dimensional blade outer ring molded lines to three dimensions according to inner surface parameters, so as to obtain intersecting lines of blades and an outer ring, wherein one embodiment can refer to the step of constructing three-dimensional blade inner ring curves according to the inner ring molded lines of the blades in the patent application of Chinese patent application No. 201410220625.9, another embodiment can further include that the two-dimensional blade outer ring molded lines are obtained by projecting three-dimensional blade outer ring molded lines, then the three-dimensional blade outer ring molded lines can be obtained by performing inverse operation of projection on the two-dimensional blade outer ring molded lines according to the inner surface parameters, another embodiment can further include that the two-dimensional blade outer ring molded lines are obtained by expanding the three-dimensional blade outer ring molded lines when the inner surface of the outer ring is expanded into a plane, and when the plane where the two-dimensional blade outer ring molded lines are located is reversely curled into the inner surface of the outer ring according to the inner surface parameters, and obtaining the three-dimensional blade outer ring molded line by the two-dimensional blade outer ring molded line.
After a two-dimensional blade outer ring skeleton line is obtained, a two-dimensional blade outer ring molded line can be obtained by constructing blade thickness distribution and superposing the thickness distribution on the two-dimensional blade outer ring skeleton line.
In this embodiment, reference may be made to an embodiment of constructing an inner ring profile of a vane of a pump impeller in chinese patent application No. 201510036723.1, reference may be made to method steps of constructing a unit vane profile in the embodiment of this patent application for constructing a two-dimensional vane outer ring profile of the present embodiment, reference may be made to method steps of constructing a vane thickness distribution and superimposing the thickness distribution on a vane profile in the embodiment of this patent application for determining a two-dimensional vane outer ring profile of a vane according to the two-dimensional vane outer ring profile, and obtaining a two-dimensional profile of the vane.
And calculating a three-dimensional blade outer ring skeleton line corresponding to the two-dimensional blade outer ring skeleton line on the inner surface of the outer ring according to the two-dimensional blade outer ring skeleton line and the inner surface parameters of the outer ring. The principle of the mode of obtaining the three-dimensional blade outer ring skeleton line by the two-dimensional blade outer ring skeleton line is the same as the principle of the implementation mode of determining the intersecting line of the blade and the outer ring 1 according to the blade outer ring molded line and the inner surface parameters of the outer ring 1.
Determining a projection vector according to the three-dimensional blade outer ring skeleton line, determining a projection plane according to the projection vector, and projecting the three-dimensional blade outer ring skeleton line on the projection plane. And taking a point set for the projection of the three-dimensional blade outer ring skeleton line on the projection plane to determine a two-dimensional blade inner ring skeleton line.
As shown in fig. 2 and 3, after the three-dimensional blade outer ring skeleton line is obtained, a suitable projection vector and a projection plane are determined for the three-dimensional blade outer ring skeleton line, and then a set of points can be selected by using the projection to produce a two-dimensional blade inner ring skeleton line. One part of the projection of the three-dimensional blade outer ring skeleton line on the projection surface can be directly used as the two-dimensional blade inner ring skeleton line, or a part of points are collected in the projection, and then a curve is constructed by adopting an interpolation method to be used as the two-dimensional blade inner ring skeleton line.
And determining a two-dimensional blade inner ring profile of the blade according to the determined two-dimensional blade inner ring skeleton line, and determining the intersection line of the blade and the inner ring according to the two-dimensional blade inner ring profile, the parameters of the projection surface and the outer surface parameters of the inner ring. The method for determining the two-dimensional blade inner ring profile of the blade according to the two-dimensional blade outer ring profile is similar to the method for determining the two-dimensional blade outer ring profile of the blade according to the two-dimensional blade inner ring profile, and the method for determining the intersection line of the blade and the inner ring according to the two-dimensional blade inner ring profile is similar to the method for determining the intersection line of the blade and the outer ring according to the blade outer ring profile.
The three-dimensional blade outer ring skeleton line is calculated by utilizing the two-dimensional blade outer ring skeleton line, then the two-dimensional blade inner ring skeleton line is determined by finding out a proper projection vector projection for the three-dimensional blade outer ring skeleton line and utilizing the projection, the proper and coordinated two-dimensional blade inner ring skeleton line can be simply and effectively obtained, the blade intersecting line of the impeller machine obtained by the method is more reasonable, coordinated and effective, and the manufactured blade has good mechanical property and good manufacturability.
As shown in FIG. 3, in some embodiments, determining a projection vector from the three-dimensional blade outer ring skeleton line comprises:
determining an extreme point of a three-dimensional blade outer ring skeleton line, connecting a starting point and an end point of the three-dimensional blade outer ring skeleton line to obtain a first line segment, and making a first straight line which is perpendicular to the connecting line and intersects with the first point through the extreme point; for the embodiment shown in fig. 3, point M is AN extreme point, points a and N are the starting point and the ending point of the three-dimensional blade outer ring skeleton line, line segment AN is the first line segment, point H is the first point, and straight line MH is the first straight line.
The radius of the over-extreme point in a plane perpendicular to the first straight line is r1A first point in a plane perpendicular to the first straight line has a radius r2Second circle of (1), wherein r1Less than r2And r is1And r2And the length of the first line segment is less than half of the length of the first line segment, a second point is taken in the first circle, a third point is taken in the second circle, and a vector obtained by connecting the second point and the third point is determined as a projection vector. For the embodiment shown in fig. 3, the s1 circle is a first circle, the s2 circle is a second circle, the M 'point is a second point, the H' point is a third point, and the vector M 'H' is the resulting projection vector. The projection vector is vertical to the projection plane, and the projection plane can be obtained according to the projection vector. The projection vector obtained by the embodiment is beneficial to enabling the projection of the obtained three-dimensional blade outer ring skeleton line to better and more completely map the three-dimensional blade outer ring skeleton line, so that the obtained two-dimensional blade inner ring skeleton line can be better coordinated with the two-dimensional blade outer ring skeleton line, and a more suitable intersecting line of the blade and the inner ring is obtained.
As shown in FIG. 3, in some embodiments, let the extreme point coordinate be (x)M，yM，zM) Let the coordinate of the first point be (x)H，yH，zH) Connecting the extreme point and the first point to obtain a first vector, and setting the space coordinate of the first vector as (V)x，Vy，Vz) Let the coordinate of the second point be (x)1，y1，z1) Let the coordinate of the third point be (x)2，y2，z2) Wherein:
Figure BDA0003288608610000091
Figure BDA0003288608610000092
y1∈(yM-r1，yM+r1)，x2∈(xH-r2，xH+r2)，y2∈(yH-r2，yH+r2). The coordinates of the projection vector of the present embodiment are determined by the above equation.
As shown in FIG. 4, in some embodiments, determining a projection vector from the three-dimensional blade outer ring skeleton line comprises:
determining an extreme point of a three-dimensional blade outer ring skeleton line, connecting a starting point and an end point of the three-dimensional blade outer ring skeleton line to obtain a first line segment, and making a first straight line which is perpendicular to the connecting line and intersects with the first point through the extreme point; for the embodiment shown in fig. 4, point M is AN extreme point, points a and N are the starting point and the ending point of the three-dimensional blade outer ring skeleton line, line segment AN is the first line segment, point H is the first point, and straight line MH is the first straight line.
And the extreme point is crossed to a plane determined by the first straight line and the first line segment to form a second straight line towards a deflection angle alpha on one side of the first straight line, and a plane perpendicular to the plane determined by the first straight line and the first line segment (the plane is a first straight line) is crossed to a first straight line to form a third straight line towards a deflection angle beta on one side of the first straight line, the second straight line and the first line segment are crossed at a fourth point, the extreme point and the fourth point are connected to obtain a second vector, a third vector is obtained according to the third straight line, and the projection vector is equal to the vector sum of the second vector and the third vector. For the embodiment shown in fig. 4, point K is the fourth point, point J is the fifth point, vector MK is the second vector, vector MJ is the third vector, and the sum of vector MK and vector MJ is the projection vector.
In some embodiments, the two-dimensional blade outer ring bone line is a bezier curve.
In some embodiments, a method for designing a blade of an impeller machine, and a method for designing a blade intersecting line of the impeller machine are also disclosed.
In some embodiments, the method of designing a blade of an impeller machine further comprises: and sweeping the intersection line of the blade and the inner ring and the intersection line of the blade and the outer ring by using a straight line to obtain the blade of the impeller machine. The method comprises the following steps of dividing the intersecting line of a blade and an inner ring and the intersecting line of the blade and an outer ring into equal parts, and then connecting the corresponding points of the intersecting line of the blade and the inner ring and the intersecting line of the blade and the outer ring to obtain the outer contour of the blade.
In some embodiments, the blade of the impeller machine is designed by applying the design method of the blade of the impeller machine.
In some embodiments, the impeller of the impeller machine comprises a blade of an impeller of a hydraulic torque converter, the hydraulic torque converter comprises an impeller, a turbine and a guide wheel, wherein the impeller comprises an impeller shell, an impeller guide ring and a blade connected between the impeller shell and the impeller guide ring, the outer ring comprises the impeller shell, and the inner ring comprises the impeller guide ring; or the blades of the impeller machine include blades of a turbine of a torque converter, the outer ring includes a turbine casing, and the inner ring includes a turbine guide ring. Thus, the inner surface parameters of the outer ring and the outer surface parameters of the inner ring may be given by giving the parameters of the torus of the torque converter.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention and not to limit it; although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art will understand that: modifications to the specific embodiments of the invention or equivalent substitutions for parts of the technical features may be made; without departing from the spirit of the present invention, it is intended to cover all aspects of the invention as defined by the appended claims.

Claims (9)

1. A method for designing a blade intersection line of an impeller machine, wherein the impeller machine comprises an outer ring, an inner ring positioned on the inner side of the outer ring and blades connected between the outer surface of the inner ring and the inner surface of the outer ring, and the method for designing the blade intersection line of the impeller machine comprises the following steps:
giving two-dimensional blade outer ring bone line, inner surface parameters of the outer ring and outer surface parameters of the inner ring;
determining a two-dimensional blade outer ring molded line of the blade according to the two-dimensional blade outer ring skeleton line, and determining an intersecting line of the blade and the outer ring according to the two-dimensional blade outer ring molded line and the inner surface parameter of the outer ring;
calculating a three-dimensional blade outer ring skeleton line corresponding to the two-dimensional blade outer ring skeleton line on the inner surface of the outer ring according to the two-dimensional blade outer ring skeleton line and the inner surface parameters of the outer ring;
determining a projection vector according to the three-dimensional blade outer ring skeleton line, determining a projection plane according to the projection vector, and projecting the three-dimensional blade outer ring skeleton line on the projection plane;
a projection point set of the three-dimensional blade outer ring skeleton line on the projection surface is taken to determine a two-dimensional blade inner ring skeleton line;
determining a two-dimensional blade inner ring molded line of the blade according to the determined two-dimensional blade inner ring skeleton line, and determining an intersection line of the blade and the inner ring according to the two-dimensional blade inner ring molded line, the parameters of the projection surface and the outer surface parameters of the inner ring.
2. The method of designing a vane intersection line of a turbomachinery as recited in claim 1, wherein determining a projection vector from said three-dimensional vane outer ring skeleton line comprises:
determining an extreme point of the three-dimensional blade outer ring skeleton line, connecting a starting point and an end point of the three-dimensional blade outer ring skeleton line to obtain a first line segment, and drawing a first straight line which is perpendicular to the connecting line and intersects with the first point through the extreme point;
radius r is made through the extreme point in a plane perpendicular to the first line1A first circle of radius r passing through the first point in a plane perpendicular to the first line2Second circle of (1), wherein r1Less than r2And r is1And r2And the length of each line segment is less than half of the length of the first line segment, a second point is taken in the first circle, a third point is taken in the second circle, and a vector obtained by connecting the second point and the third point is determined as the projection vector.
3. The method of designing the intersecting line of the vanes of the turbomachinery as recited in claim 2, wherein the coordinate of said extreme point is (x)M，yM，zM) Let the coordinates of the first point be (x)H，yH，zH) Connecting the extreme point and the stationThe first point obtains a first vector, and the space coordinate of the first vector is (V)x，Vy，Vz) Let the coordinates of the second point be (x)1，y1，z1) Let the coordinate of the third point be (x)2，y2，z2) Wherein:
Figure FDA0003288608600000021
Figure FDA0003288608600000022
x1∈(xM-r1，xM+r1)，
y1∈(yM-r1，yM+r1)，x2∈(xH-r2，xH+r2)，y2∈(yH-r2，yH+r2)。
4. the method of designing a vane intersection line of a turbomachinery as recited in claim 1, wherein determining a projection vector from said three-dimensional vane outer ring skeleton line comprises:
determining an extreme point of the three-dimensional blade outer ring skeleton line, connecting a starting point and an end point of the three-dimensional blade outer ring skeleton line to obtain a first line segment, and drawing a first straight line which is perpendicular to the connecting line and intersects with the first point through the extreme point;
and passing the extreme point to make a second straight line towards a deflection angle alpha on one side of the first straight line in a plane determined by the first straight line and the first line segment, and to make a third straight line towards a deflection angle beta on one side of the first straight line in a plane perpendicular to the plane determined by the first straight line and the first line segment, wherein the second straight line and the first line segment are intersected at a fourth point, the extreme point and the fourth point are connected to obtain a second vector, a third vector is obtained according to the third straight line, and the projection vector is equal to the vector sum of the second vector and the third vector.
5. The method for designing the intersecting line of the blade of the turbomachinery as recited in any one of claims 1 to 4, wherein the two-dimensional blade outer circumferential skeleton line is a bezier curve.
6. A method for designing a blade of an impeller machine, comprising the method for designing the intersecting line of the blade of the impeller machine according to any one of claims 1 to 5.
7. The method of designing a vane for an impeller machine according to claim 6, further comprising: and sweeping the intersecting line of the blade and the inner ring and the intersecting line of the blade and the outer ring by using a straight line to obtain the blade of the impeller machine.
8. A vane for an impeller machine, characterized by comprising a design by applying the method for designing a vane for an impeller machine according to claim 6 or 7.
9. The turbomachine blade of claim 8, wherein said turbomachine blade comprises a blade of an impeller of a torque converter, said outer ring comprises an impeller casing, and said inner ring comprises an impeller guide ring; or the impeller machine blades comprise blades of a turbine of a hydrodynamic torque converter, the outer ring comprises a turbine casing, and the inner ring comprises a turbine guide ring.
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